Turbine airfoil cooling system with divergent film cooling hole

Fluid reaction surfaces (i.e. – impellers) – With heating – cooling or thermal insulation means – Changing state mass within or fluid flow through working...

Reexamination Certificate

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C416S09700R, C416S23100A

Reexamination Certificate

active

08079810

ABSTRACT:
A cooling system for a turbine airfoil of a turbine engine having at least one divergent film cooling hole positioned in an outer wall defining the turbine airfoil is disclosed. The divergent film cooling hole includes a first section extending from an inner surface of the outer wall into the outer wall and a second section extending the first section and terminating at an outer surface of the outer wall. The divergent film cooling hole may provide a metering capability together with a divergent section that provides a larger film cooling hole breakout and footprint, which creates better film coverage and yields better cooling of the turbine airfoil. The divergent film cooling hole may provide a smooth transition, which allows the film cooling flow to diffuse better in the second section of the divergent film cooling hole.

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